Aircraft engine sealing device

Abstract

The utility model discloses an aero-engine sealing device, which belongs to the technical field of sealing and comprises a first aero-engine shell, an aero-engine is fixedly mounted in the first aero-engine shell, and a sealing component is arranged in the aero-engine. A quick release assembly is arranged outside the shell of the first shell of the aero-engine; in the utility model, through the design, the function of sealing the bearing cavity when the rotating speed of the rotor is low or high is realized, the aero-engine can be conveniently disassembled and checked when the aero-engine breaks down, and the problem that the aero-engine is inconvenient to check when the aero-engine breaks down due to the fact that the sealing devices are complex and tedious to install is avoided. And most sealing devices conduct sealing through rotation of a rotating shaft, however, when the aero-engine just starts to start, the speed of the rotating shaft is low, and the situation that lubricating oil leaks possibly occurs.

Description

Technical Field

[0001] The utility model belongs to the technical field of sealing, and in particular relates to a sealing device for an aero-engine. Background Art

[0002] For an airplane, the aircraft engine is a very important device. During the flight of the aircraft, the rotation speed of the aircraft engine rotor is very high, so it is very important to ensure the normal and stable operation of the rotor during flight. The lubrication of the engine rotor bearing and the sealing effect in the bearing cavity determine whether the aircraft engine can operate normally.

[0003] Although there are various aircraft engine sealing devices on the market today, these devices are complicated and cumbersome to install, and it is inconvenient to check when problems occur. Most of the sealing devices rely on the rotation of the shaft to seal, but when the aircraft engine is just started, the speed of the shaft is slow, and the sealing effect of the sealing device at this time is not good, which may cause leakage of lubricating oil and affect the operation of the aircraft engine. In order to solve the above problems, an aircraft engine sealing device is urgently needed to solve the above problems. Utility Model Content

[0004] The purpose of the utility model is to solve the problem that although there are various aircraft engine sealing devices on the market nowadays, these devices are relatively complicated and cumbersome to install, and it is inconvenient to check when problems occur. Most of the sealing devices rely on the rotation of the shaft to seal, but when the aircraft engine is just started, the speed of the shaft is slow, and the sealing effect of the sealing device is not good at this time, which may cause leakage of lubricating oil and affect the operation of the aircraft engine. A sealing device for an aircraft engine is proposed.

[0005] In order to achieve the above-mentioned purpose, the utility model adopts the following technical scheme: an aircraft engine sealing device, comprising a first outer shell of an aircraft engine, an aircraft engine is fixedly installed inside the first outer shell of the aircraft engine, a sealing component is arranged inside the aircraft engine, and a quick-release component is arranged outside the outer shell of the first outer shell of the aircraft engine.

[0006] As a further description of the above technical solution:

[0007] The sealing component comprises a bearing cavity. The interior of the aircraft engine is provided with a bearing cavity, and a sealing ring is fixedly mounted on the outer wall of the bearing cavity.

[0008] As a further description of the above technical solution:

[0009] The outer wall of the bearing cavity is provided with a ventilation hole, and the bearing cavity is slidably connected with a sliding shaft through a sliding hole provided inside the bearing cavity, and a limiting disk is fixedly installed at the bottom end of the sliding shaft.

[0010] As a further description of the above technical solution:

[0011] The quick-release assembly includes a first connecting frame, a plug block is fixedly mounted on one side of the first connecting frame, a bolt is threadedly connected to the first connecting frame through a threaded hole arranged on one side of the first connecting frame, and a nut is threadedly connected to the outer wall of the bolt.

[0012] As a further description of the above technical solution:

[0013] A second connecting frame is fixedly mounted on one end of the nut. The second connecting frame is plugged into the plug block via a slot arranged on one side surface of the second connecting frame. A second outer shell of the aircraft engine is fixedly mounted on the bottom surface of the second connecting frame.

[0014] As a further description of the above technical solution:

[0015] The second connecting frame is threadedly connected with a bolt through a threaded hole arranged inside it, a wax block is fixedly installed on one end of the bolt, a wax block is fixedly installed on one side surface of the first connecting frame, and two quick-release components are symmetrically arranged about the transverse central symmetry axis of the first outer shell of the aircraft engine and the second outer shell of the aircraft engine.

[0016] In summary, due to the adoption of the above technical solution, the beneficial effects of the utility model are:

[0017] 1. In the utility model, by providing a sealing component and a quick-release component, when the device is used, if a fault occurs inside the aircraft engine and needs to be checked, the bolt can be rotated out, and then the first connecting frame and the second connecting frame are separated. With the separation of the first connecting frame and the second connecting frame, the first outer shell of the aircraft engine and the second outer shell of the aircraft engine are also separated, so that it is convenient for people to check the aircraft engine. When the engine is just started, external air enters the engine, and then the air enters the cavity in the bearing through the ventilation hole, so that the oil blocking mechanism is squeezed, so that the bearing cavity is sealed, and after the speed of the rotor is increased, the numerous sliding shafts are centrifugal. Under the action, it slides out of the bearing cavity and forms a labyrinth seal with the sealing ring. Through this design, not only the function of sealing the bearing cavity when the rotor speed is low or high is realized, but also it is convenient to disassemble and inspect the aircraft engine when it fails, avoiding the problem that these sealing devices are complicated and cumbersome to install, which makes it inconvenient to check when problems occur. Most of the sealing devices rely on the rotation of the shaft to seal, but when the aircraft engine is just started, the speed of the shaft is slow, and the sealing effect of the sealing device is not good at this time, which may cause leakage of lubricating oil and affect the operation of the aircraft engine. In addition, it is simple and convenient to use and has strong practicality.

[0018] 2. In the utility model, by providing a wax block, the bolts can be fixed again during the use of the device, so that the first connection and the second connection frame become more stable, and at the same time the service life of the bolts is increased, so that they are protected from erosion by rain and the like, so that they do not need to be replaced frequently, and subsequent disassembly and installation are also convenient, which is more environmentally friendly, simple and convenient to use, and highly practical. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 This is a three-dimensional structural schematic diagram of an aircraft engine sealing device proposed by the utility model;

[0020] Figure 2 This is a schematic diagram of the exploded three-dimensional structure of an aircraft engine sealing device proposed by the utility model;

[0021] Figure 3 This is an exploded three-dimensional structural schematic diagram of a sealing component in an aero-engine sealing device proposed by the utility model;

[0022] Figure 4 The utility model is a schematic diagram of an exploded three-dimensional structure of a quick-release component in an aero-engine sealing device.

[0023] Legend:

[0024] 1. First outer shell of aircraft engine; 2. Aircraft engine; 3. Quick-release assembly; 31. First connecting frame; 32. Insert block; 33. Second connecting frame; 34. Wax block; 35. Bolt; 36. Nut; 4. Second outer shell of aircraft engine; 5. Sealing assembly; 51. Sliding shaft; 52. Limiting plate; 53. Bearing cavity; 54. Ventilation hole; 55. Sealing ring. DETAILED DESCRIPTION

[0025] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments of the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0026] See also Figure 1-4 The utility model provides a technical solution: an aircraft engine sealing device, comprising an aircraft engine first shell 1, an aircraft engine 2 is fixedly installed inside the aircraft engine first shell 1, a sealing component 5 is arranged inside the aircraft engine 2, and a quick-release component 3 is arranged outside the shell of the aircraft engine first shell 1;

[0027] The sealing component 5 includes a bearing cavity 53, a bearing cavity 53 is provided inside the aircraft engine 2, a sealing ring 55 is fixedly installed on the outer wall of the bearing cavity 53, a ventilation hole 54 is provided on the outer wall of the bearing cavity 53, the bearing cavity 53 is slidably connected with a sliding shaft 51 through a sliding hole provided inside the bearing cavity 53, a limiting plate 52 is fixedly installed on the bottom end of the sliding shaft 51, the quick release component 3 includes a first connecting frame 31, an insert block 32 is fixedly installed on one side surface of the first connecting frame 31, the first connecting frame 31 is threadedly connected with a bolt 35 through a threaded hole provided on one side surface thereof, a nut 36 is threadedly connected on the outer wall of the bolt 35, a second connecting frame 33 is fixedly installed on one end of the nut 36, the second connecting frame 33 is plugged with the insert block 32 through a slot provided on one side surface thereof, and the second outer shell 4 of the aircraft engine is fixedly installed on the bottom surface of the second connecting frame 33;

[0028] The specific implementation method is as follows: when the device is used, if a fault occurs inside the aircraft engine 2 and needs to be checked, the bolt 35 can be rotated out, and then the first connecting frame 31 and the second connecting frame 33 are separated. As the first connecting frame 31 and the second connecting frame 33 are separated, the first outer shell 1 of the aircraft engine and the second outer shell 4 of the aircraft engine are also separated, so that it is convenient for people to check the aircraft engine 2. When the engine is just started, external air enters the engine, and then the air enters the cavity in the bearing through the ventilation hole 54, so that the oil blocking mechanism is squeezed, so that the bearing cavity 53 is sealed. After the rotation speed of the rotor is increased, the plurality of sliding shafts 51 slide out of the bearing cavity 53 under the action of centrifugal force, and form a labyrinth seal with the sealing ring 55.

[0029] The second connecting frame 33 is threadedly connected with a bolt 35 through a threaded hole set inside it, and a wax block 34 is fixedly installed on one end of the bolt 35. A wax block 34 is fixedly installed on one side surface of the first connecting frame 31. Two quick-release components 3 are symmetrically arranged about the transverse central symmetry axis of the first outer shell 1 and the second outer shell 4 of the aircraft engine.

[0030] The specific implementation method is as follows: during the use of the device, the bolt 35 can be re-fixed to make the first connection and the second connection frame 33 more stable, while increasing the service life of the bolt 35, protecting it from erosion by rain and the like, eliminating the need for frequent replacement, and facilitating subsequent disassembly and installation, making it more environmentally friendly to use.

[0031] Working principle: When the device is used, if a fault occurs inside the aircraft engine 2 and needs to be checked, the bolt 35 can be rotated out, and then the first connecting frame 31 and the second connecting frame 33 are separated. As the first connecting frame 31 and the second connecting frame 33 are separated, the first outer shell 1 of the aircraft engine and the second outer shell 4 of the aircraft engine are also separated, so that people can check the aircraft engine 2 conveniently. When the engine is just started, external air enters the engine, and then the air enters the cavity in the bearing through the ventilation hole 54, so that the oil blocking mechanism is squeezed and the bearing cavity 53 is sealed. After the speed of the rotor is increased, the numerous sliding shafts 51 slide out of the bearing cavity 53 under the action of centrifugal force, and form a labyrinth seal with the sealing ring 55. During the use of the device, the bolt 35 can be fixed again, so that the first connection and the second connecting frame 33 become more stable, and at the same time, the service life of the bolt 35 is increased, so that it is protected from erosion by rain and the like, so that it does not need to be replaced frequently, and it is also convenient for subsequent disassembly and installation, which is more environmentally friendly to use.

[0032] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can make equivalent replacements or changes within the technical scope disclosed by the present invention according to the technical scheme and the utility model concept of the present invention, which should be covered by the protection scope of the present invention.

Claims

1. An aircraft engine sealing device, comprising a first casing (1) of the aircraft engine, characterized in that: An aircraft engine (2) is fixedly installed inside the first outer shell (1) of the aircraft engine, a sealing component (5) is arranged inside the aircraft engine (2), and a quick-release component (3) is arranged outside the outer shell of the first outer shell (1) of the aircraft engine.

2. An aircraft engine sealing device according to claim 1, characterized in that: The sealing assembly (5) comprises a bearing cavity (53). The interior of the aircraft engine (2) is provided with the bearing cavity (53). A sealing ring (55) is fixedly mounted on the outer wall of the bearing cavity (53).

3. An aircraft engine sealing device according to claim 2, characterized in that: A ventilation hole (54) is provided on the outer wall of the bearing cavity (53); the bearing cavity (53) is slidably connected to a sliding shaft (51) through a sliding hole provided inside the bearing cavity (53); a limiting plate (52) is fixedly mounted on the bottom end of the sliding shaft (51).

4. An aircraft engine sealing device according to claim 3, characterized in that: The quick-release assembly (3) comprises a first connecting frame (31), an insert block (32) is fixedly mounted on one side surface of the first connecting frame (31), a bolt (35) is threadedly connected to the first connecting frame (31) through a threaded hole provided on one side surface thereof, and a nut (36) is threadedly connected to the outer wall of the bolt (35).

5. An aircraft engine sealing device according to claim 4, characterized in that: A second connecting frame (33) is fixedly mounted on one end of the nut (36); the second connecting frame (33) is plugged into the plug block (32) via a slot provided on one side surface thereof; and a second casing (4) of the aircraft engine is fixedly mounted on the bottom surface of the second connecting frame (33).

6. An aircraft engine sealing device according to claim 5, characterized in that: The second connecting frame (33) is threadedly connected to a bolt (35) through a threaded hole provided therein, a wax block (34) is fixedly mounted on one end of the bolt (35), a wax block (34) is fixedly mounted on one side surface of the first connecting frame (31), and two quick-release assemblies (3) are symmetrically arranged about the transverse central symmetry axis of the first outer shell (1) of the aircraft engine and the second outer shell (4) of the aircraft engine.

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